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E61 (5.64%) (e61-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E61 (5.64%) (e61-il)
Reynolds number: 200,000
Max Cl/Cd: 112.53 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e61-il-200000.txt
Download as CSV file: xf-e61-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E61  (5.64%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.250  -0.2615   0.10287   0.09979  -0.0437   0.9726   0.0193
  -6.000  -0.2533   0.09717   0.09409  -0.0416   0.9703   0.0202
  -5.750  -0.2431   0.09370   0.09063  -0.0420   0.9644   0.0210
  -5.500  -0.2205   0.09002   0.08693  -0.0467   0.9607   0.0218
  -5.250  -0.2069   0.08699   0.08388  -0.0494   0.9537   0.0226
  -5.000  -0.1817   0.08312   0.08000  -0.0551   0.9493   0.0239
  -4.750  -0.1619   0.07977   0.07664  -0.0595   0.9430   0.0250
  -4.500  -0.1332   0.07592   0.07277  -0.0662   0.9381   0.0264
  -4.250  -0.0780   0.07133   0.06810  -0.0810   0.9355   0.0290
  -4.000  -0.0274   0.06770   0.06437  -0.0944   0.9281   0.0298
  -3.750   0.0019   0.06145   0.05810  -0.1006   0.9254   0.0309
  -3.500   0.0221   0.05840   0.05506  -0.1011   0.9233   0.0335
  -3.250   0.0552   0.05517   0.05177  -0.1068   0.9179   0.0366
  -3.000   0.1365   0.04862   0.04497  -0.1259   0.9165   0.0443
  -2.750   0.1689   0.04599   0.04231  -0.1293   0.9136   0.0496
  -2.500   0.2511   0.04014   0.03611  -0.1460   0.9137   0.0584
  -2.250   0.3197   0.03619   0.03174  -0.1575   0.9134   0.0711
  -2.000   0.3583   0.03379   0.02936  -0.1613   0.9120   0.0773
  -1.750   0.4209   0.03080   0.02589  -0.1703   0.9118   0.0996
  -1.500   0.4641   0.02895   0.02401  -0.1745   0.9107   0.1188
  -1.250   0.5432   0.02358   0.01733  -0.1836   0.9126   0.0519
  -1.000   0.5909   0.02185   0.01501  -0.1870   0.9117   0.0434
  -0.750   0.6334   0.02086   0.01383  -0.1897   0.9104   0.0423
  -0.500   0.6775   0.01958   0.01246  -0.1929   0.9095   0.0434
  -0.250   0.7042   0.01919   0.01211  -0.1930   0.9021   0.0503
   0.000   0.7454   0.01856   0.01143  -0.1955   0.8996   0.0582
   0.250   0.7921   0.01738   0.01107  -0.1998   0.8984   0.3490
   0.500   0.8245   0.01592   0.01071  -0.2001   0.8967   1.0000
   0.750   0.8502   0.01598   0.01065  -0.1996   0.8886   1.0000
   1.000   0.8895   0.01560   0.01016  -0.2016   0.8858   1.0000
   1.250   0.9313   0.01510   0.00958  -0.2041   0.8840   1.0000
   1.500   0.9602   0.01499   0.00944  -0.2041   0.8768   1.0000
   1.750   1.0001   0.01451   0.00892  -0.2061   0.8732   1.0000
   2.000   1.0453   0.01391   0.00831  -0.2092   0.8707   1.0000
   2.250   1.0764   0.01372   0.00812  -0.2096   0.8627   1.0000
   2.500   1.1207   0.01319   0.00765  -0.2125   0.8580   1.0000
   2.750   1.1539   0.01297   0.00745  -0.2133   0.8492   1.0000
   3.000   1.1976   0.01250   0.00700  -0.2161   0.8426   1.0000
   3.250   1.2278   0.01239   0.00693  -0.2163   0.8309   1.0000
   3.500   1.2593   0.01226   0.00689  -0.2166   0.8181   1.0000
   3.750   1.2904   0.01218   0.00685  -0.2169   0.8042   1.0000
   4.000   1.3210   0.01213   0.00683  -0.2171   0.7887   1.0000
   4.250   1.3467   0.01219   0.00693  -0.2162   0.7699   1.0000
   4.500   1.3730   0.01226   0.00707  -0.2154   0.7488   1.0000
   4.750   1.3965   0.01241   0.00725  -0.2141   0.7249   1.0000
   5.000   1.4189   0.01261   0.00746  -0.2126   0.6978   1.0000
   5.250   1.4398   0.01288   0.00769  -0.2107   0.6642   1.0000
   5.500   1.4528   0.01337   0.00793  -0.2071   0.6007   1.0000
   5.750   1.4563   0.01446   0.00841  -0.2018   0.5011   1.0000
   6.000   1.4582   0.01583   0.00921  -0.1966   0.4114   1.0000
   6.250   1.4619   0.01718   0.01018  -0.1921   0.3342   1.0000
   6.500   1.4635   0.01877   0.01124  -0.1874   0.2510   1.0000
   6.750   1.4679   0.02042   0.01242  -0.1835   0.1733   1.0000
   7.000   1.4671   0.02280   0.01407  -0.1789   0.0751   1.0000
   7.250   1.4666   0.02544   0.01632  -0.1739   0.0254   1.0000
   7.500   1.4733   0.02731   0.01830  -0.1702   0.0190   1.0000
   7.750   1.4845   0.02869   0.01984  -0.1673   0.0170   1.0000
   8.000   1.4927   0.03037   0.02170  -0.1640   0.0158   1.0000
   8.250   1.5000   0.03225   0.02373  -0.1607   0.0149   1.0000
   8.500   1.5077   0.03430   0.02592  -0.1575   0.0143   1.0000
   8.750   1.5175   0.03655   0.02836  -0.1547   0.0140   1.0000
   9.000   1.5320   0.03904   0.03101  -0.1526   0.0138   1.0000
   9.250   1.5553   0.04196   0.03416  -0.1516   0.0139   1.0000
   9.500   1.5894   0.04617   0.03880  -0.1519   0.0146   1.0000
   9.750   1.6149   0.05144   0.04464  -0.1511   0.0157   1.0000
  10.000   1.6222   0.05674   0.05045  -0.1482   0.0168   1.0000
  10.250   1.6182   0.06210   0.05623  -0.1443   0.0177   1.0000
  10.500   1.6158   0.06957   0.06457  -0.1387   0.0242   1.0000
  10.750   1.4781   0.06956   0.06470  -0.1201   0.0177   1.0000
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